DE3420441A1 - CONTROL DEVICE FOR AIRCRAFT - Google Patents

Description

Patent department

9550

Control device for aircraft

The invention relates to a control device for aircraft, with a device for deflecting the Engine jet, which consists of a cross-shaped and pivotable thruster arranged on the engine nozzle.

Such control devices are used to control aircraft propelled by jet engines, such as missiles or aircraft used, whereby by a deflection of the engine beam on the aircraft Control torques can be generated.

A control device of this type is from the DE-PS 19 64 205 became known. According to this it is provided that initially swiveling engine nozzles by means of engine jet deflection over a flight attitude deviation control a position controller and then adjust the aerodynamic control surfaces for this purpose, while the engine nozzles staggered back to their original position will.

However, this control device is on the one hand with regard to the design of the pivotable engine nozzles very expensive and on the other hand neither suitable nor suitable for improving the flight safety of aircraft

intended.
30th

The invention is based on the object of a control device of the type mentioned above to propose that an aircraft automatically disengages from one suddenly

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3420U1

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Patent department

9550

occurring aerodynamically unstable or · only partially controllable position in a stable position or move the target position around the pitch, yaw and ro11 axes can and thus increases the flight safety of aircraft while avoiding the disadvantages mentioned above .

This object is achieved by the features cited in the characterizing part of claim 1. 10

Further advantageous refinements emerge from the subclaims.

An embodiment of the invention is shown in the drawing and is described in more detail below. Show it

1 shows a view of an aircraft with aerodynamic control surfaces on the wings and on the tail as well as cross-shaped thrusters

the engine nozzle

Fig. 2 is a block diagram of the control unit.

The aircraft 1 shown in FIG. 1 is provided on the wings 2 and on the tail 3 with aerodynamic control surfaces 4 ₃ 5j 6, 7, 8 - hereinafter referred to only as control surfaces. At the stern 3, an engine nozzle 9 is provided with a device 9a, which consists of four thrusters 11, 12, 13j 14 pivotable about its longitudinal axis 10, each with an actuator 15, only indicated in FIG. 1, which is cross-shaped on the engine nozzle 9 are arranged. For minimal uptake

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Patent department

9550

wall with a similar control effect can be done in a manner not shown by a star-shaped arrangement of only three thrusters 11, 12, 13 on the engine nozzle 9. With these, on the one hand, a deflection of the engine jet 16 of an engine, not shown, can be achieved in the required axial directions and, on the other hand, by means of their common deflection in one direction - for example clockwise - the engine jet 16 can also be in a
Dra11 movement are offset, whereby control torques for roll control - in this case counterclockwise - of the aircraft 1 can be generated.

The thrusters 11, 12, 13, 14 are lengthwise, i.e.

running parallel to its longitudinal axis 10 only in a l / 2 to 2/3 length of the radius of the engine nozzle 9, in order to prevent that for reasons of service life
they protrude into the very hot core 17 of the engine jet l6 and experience damage there. It has

namely shown that the engine jet 16 in
The area of the periphery of the engine nozzle 9 has a significantly lower temperature than in its core 17. Neither the mounting of the thrusters 11, 12, 13 , 14 nor the design of their actuators 15 ₃ di <> correspond to the oinor control unit 18 are the subject of the invention.

In FIG. 2, a block diagram of the electronic control unit 18 is shown, which is used for regulation and in-flight attitude control from one

Position controller 19 consists in a known manner with an actual value transmitter 20, a set position value transmitter 21, a

Patent department

3420U1

9550

nem dynamic pressure transducer 22 and with a control value transducer 23 for the purpose of signal processing for the control of the control surfaces 4> 5, ό, 7 »8 by means of a further actuator 24 is connected. The control value generator 23 serves to determine the angle of incidence ροκ i (.. i on and ^{drt x} grunt of the approach I 1 wi nke I path of the control surfaces 4? 5 ₃ 6, 7, 8 Adjusting forces are measured in relation to the permissible adjusting forces for the aforementioned control surfaces for transmission to the position controller 19.

In addition, the actuators 15 for controlling the thrusters 11, 12, 13, 14 and a '- ¹ control device 25 for controlling the engine thrust are connected to the position controller 19.

The operation of the control device is like

follows:
20th

If the position controller 19 of the control unit 18 determines through the ongoing signal comparison between the target position value transmitter 21 and the actual position value transmitter 20, that to control or regulate the aircraft 1 from the actual position to the target position, which is determined by the control surfaces 4, _3, 5, 6, 7? 8 generated control torques are no longer sufficient, the thrusters 11, 12, 13, 14 are automatically controlled by the position controller 19 to a corresponding angle of attack and the missing control torques are generated in a known manner by deflecting the engine jet 16.

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Patent department

9550

In the event of a complete failure of the control surface effectiveness, such as, for example, due to a component failure or in an excessive flight condition, etc., the entire control function for the aircraft 1 can be completely taken over by the thrusters 11, 12, 13, 14. Likewise, the thrusters 11, 12, 13, 14 in addition to the control surfaces 4 , 53, 6, 7, 8 can be brought into action for the implementation of faster flight maneuvers.

^ O To control the aircraft 1 with the control device 18 are continuously updated by means of the control value transmitter 23 of the control unit 18 the current angle of attack position and / or the actuating forces of the control surfaces 43 53 6, 73 8 as well as the dynamic pressure size of the position controller 19 transferred. With reference to (Mi) OIi, this determines predetermined dynamic pressure-dependent control torque values on the tax effectiveness to be provided in order to control the aircraft from the actual to the target position to be able to. In the case of insufficient or missing

20th

Control effectiveness of the control surfaces 4, _3, 5, _3, 6, 7, 8, the thrusters 11, 12, 13, 14 are automatically controlled via the actuators 15 to the engine jet l6 that with the resulting jet deflection

the sum of the required steering torques the pre-25

given control torque curve for the target position to be achieved of the aircraft 1 corresponds.

With FIi If e control 1 device 2 5, the position controller

19 also with insufficient control effect 30

degree of the thrusters 11, 12, 13, 14 the engine thrust of the aircraft selected by the pilot or autopilot 1 automatically increase in order to increase their tax effectiveness on their own or together with the tax areas

35

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Patent department

chen 4j 5, 6, 7, 8 to adapt the control torque curve specified in the position controller 19 in accordance with the aircraft's target position.

The advantages of the proposed invention are in particular that aircraft on simple and safe way from an aerodynamically uncontrollable or only partially aerodynamically controllable Flight status automatically to a flight behavior that can be controlled and regulated at any time using a brought considerable excess of control capacity can be. The safety factor that can be achieved thereby makes a considerable contribution

for flight safety.
15th

This means that for emergency situations, such as those that are often not uncritical, for example during the Landing approach of an aircraft occur for this

essential and automatically quick-reacting controls

and control reserves are available for all flight axes. In addition, the engine thrust excess, which results from the low thrust requirement for the aircraft during the landing process, for further additional tax purposes both in the 1 luge and can also be used on the ground for the taxiing phase of the aircraft on the airfield.

Claims (5)

05/30/1984 Ka / th patent department Q ς ς ο control device for aircraft patent claims 1. Control device for aircraft with a Device for deflecting the engine jet, consisting of and arranged in a cross shape on the engine nozzle. There is a thruster pivotable about its longitudinal axis, characterized in that the thruster (11, 12, 13, 14) for the pitch, yaw and roll movements of the aircraft (1) by means of a control unit (18) can be automatically regulated in such a way that they control the control torques of the aerodynamic control surfaces (4j 5, 6, 7j 8) of the aircraft (1) or at replace their failure. 2. Control device according to claim 1, characterized by the fact that the thrusters (11, 12, 13, 14) are adjustable so that the sum of the control torques for the pitch, yaw and roll movement of the aircraft (1) from the The control torques of the thrusters (11, 12, 13, 14) and those of the aerodynamic control surfaces (4> 5 ₃ 6, 7> 8) each correspond to a predetermined course as a function of the dynamic pressure of the aircraft (I). Patent department 9550 3 · Control device according to claims 1 and 2, characterized in that the control unit (L8) to increase the control effectiveness of the thrusters (11, 12, 13, 14) a control device (25) for an automatic engine thrust control . 4- control device according to one or more of the preceding claims, characterized g e k e η η that on the engine nozzle (9) three Thrusters (11, 12, 13) are arranged in a star shape, which can be regulated so that one of the aircraft (1) Pitch, yaw and roll movements can be carried out individually or in combination. 5. Control device according to one or more of the preceding claims, characterized in that g e k e η η ze Ichnet that the thrusters (11, 12, 13, 14) to increase the service life only one in length 1/2 to 2/3 length of the radius of the engine nozzle (9) executed and on this to avoid the hot core (17) of the engine jet (16) from its periphery are arranged starting.